CN105423341A - Pre-mixing low-emission gas turbine combustion chamber with permanent flame - Google Patents
Pre-mixing low-emission gas turbine combustion chamber with permanent flame Download PDFInfo
- Publication number
- CN105423341A CN105423341A CN201511007113.5A CN201511007113A CN105423341A CN 105423341 A CN105423341 A CN 105423341A CN 201511007113 A CN201511007113 A CN 201511007113A CN 105423341 A CN105423341 A CN 105423341A
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- combustion chamber
- flame
- shell
- gas turbine
- inner liner
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
- F23R3/18—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants
- F23R3/20—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants incorporating fuel injection means
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
Abstract
The invention discloses a pre-mixing low-emission gas turbine combustion chamber with permanent flame and relates to gas turbine combustion chambers. The pre-mixing low-emission gas turbine combustion chamber comprises igniters, outer shells, flame tubes and pre-mixing sections. The combustion chamber is composed of sixteen independent igniters. Each igniter comprises an outer shell, a flame tube, a permanent nozzle and two air adjusting valves. Flow guide plates, by-pass pipes and the air adjusting valves are installed on the outer shells. One ends of the by-pass pipes are installed on the outer shells, and the other ends of the by-pass pipes are installed at the tails of the flame tubes. The air adjusting valves are connected with the by-pass pipes and located outside the outer shells. The permanent nozzles and the flame tubes are located inside the outer shells. The pre-mixing sections and the flame tubes are provided with ring pipes and hydrocyclones respectively. The ring pipes are connected with the pre-mixing sections. The permanent nozzles are installed on the flame tubes. The flame tubes and the flow guide plates form cooling zones, the wall face temperature of the flame tubes can be effectively lowered and the service life of the combustion chamber is prolonged. The pre-mixing low-emission gas turbine combustion chamber can be applied to electrical, petrochemical and other industrial gas turbines with natural gas as fuel.
Description
technical field:
The present invention relates to gas-turbine combustion chamber, be specifically related to a kind of premixed low emission gas turbine combustion chamber having flame on duty.
background technology:
Gas turbine is since last century, early forties came out, there is because of it series of advantages such as power is large, efficiency is high, volume is little, starting is fast, smooth running, manipulation is simple, maintaining is convenient, reliable operation, in short over half a century, achieved the development of advancing by leaps and bounds, the numerous areas such as the electric power in countries in the world, petrochemical industry, traffic, metallurgy, military affairs obtains increasingly extensive application.The height of gas turbine technology level has now become one of important symbol of a national science and technology level and military strength.Along with the variation of variety of energy sources, the going from bad to worse of the extensive use of gas turbine and environmental pollution, the environmental protection ideas of people strengthens day by day, and more and more stricter pollutant emission standard is constantly released in countries in the world.Industry gas turbine is to pollutant, and especially more strict to the emission request of NOx and CO, low emission has become one of important performance indexes of advanced gas turbine.Control for realizing gas turbine low emission, combustion chamber generally adopts lean fuel premixed combustion technology, but can directly cause combustion zone temperature lower, combustion stability is just deteriorated, easily flame-out danger occurs.The greatest problem that lean fuel premixed combustion technology faces is exactly that combustion stability declines, the change of the tempering in premix chamber and the change of load or fuel value and composition occurs flame-out.For solving problems, can introduce flame on duty, effectively can improve the stability of flame in combustion chamber, therefore research has the premixed low emission combustor of flame on duty to have important using value.
summary of the invention:
The present invention is that the easy lean combustion in conventional combustion chamber contamination thing discharge capacity high or low discharge combustion chamber is stopped working, the problem of poor reliability in order to solve, and a kind of premixed low emission gas turbine combustion chamber having flame on duty is provided, it is easy to use, simple to operate, be easy to large-scale promotion application.
The technical solution used in the present invention is: a kind of premixed low emission gas turbine combustion chamber having flame on duty, comprise igniter, shell, burner inner liner and premix section, combustion chamber is made up of 16 separate igniter, separate igniter comprises a shell, a burner inner liner, a nozzle on duty and two air control valves, shell is provided with deflector, bypass pipe and air control valve, described bypass pipe one end is installed on shell, the bypass pipe other end is installed on flame drum tail, described air control valve is connected with bypass pipe, and air control valve is positioned at housing exterior, described nozzle on duty, burner inner liner is positioned at enclosure, premix section, burner inner liner is provided with endless tube and cyclone, endless tube is connected with premix section, burner inner liner is provided with nozzle on duty, salband is formed between burner inner liner and deflector, ring cavity C is formed between deflector and shell, on shell, mounting guiding board position circumference is distributed with vibration damping hole, whole combustion chamber is provided with two igniters, flame tube interconnector is adopted to connect between two consecutive points firearms.
Described premix section is provided with four main gas outlets and four main gas outlets are evenly distributed in premix section.
Described endless tube is connected with main fuel gas inlet.
The invention has the beneficial effects as follows: 1, combustion chamber adopts the Split type structure of 16 separate igniter, be convenient to realize the maintenance to each separate igniter and replacing;
2, combustion chamber adopts with nozzle on duty, by introducing flame on duty, effectively can improve the stability of flame;
3, form resonator between deflector and shell, on shell, mounting guiding board position circumference is distributed with vibration damping hole, effectively reduces igniter pressure fluctuation, improves combustion chamber service life and combustibility;
4, combustion chamber adopts twice premix to combine, and realizes combustion gas and first mixes after-combustion with air, ensure combustion chambers burn performance;
5, conventional combustion room air control valve is generally arranged in combustion chamber, is high-temperature component, its poor reliability, and safeguard comparatively difficulty, this device air control valve is positioned at outside, combustion chamber, is non high temperature parts, effectively improves combustion chamber operational reliability and is convenient to safeguard and change;
6, combustion chamber utilizes air conditioning valve regulation to enter combustion zone air capacity, effectively can realize the object of pollutant low emission;
7, the salband that formed of burner inner liner and deflector, can effective cooling flame tube wall surface temperature, improves combustion chamber service life;
8, the present invention can be applicable on the industry gas turbine that electric power, petrochemical industry etc. take natural gas as fuel.
accompanying drawing illustrates:
Fig. 1 is structural representation of the present invention.
Fig. 2 is A-A sectional view of the present invention.
detailed description of the invention:
With reference to each figure, a kind of premixed low emission gas turbine combustion chamber having flame on duty, comprise igniter, shell, burner inner liner and premix section, combustion chamber is made up of 16 separate igniter, separate igniter comprises a shell 4, a burner inner liner 5, a nozzle 1 on duty and two air control valves 7, shell 4 is provided with deflector 8, bypass pipe 6 and air control valve 7, described bypass pipe 6 one end is installed on shell 4, bypass pipe 6 other end is installed on burner inner liner 5 afterbody, described air control valve 7 is connected with bypass pipe 6, and air control valve 7 is positioned at shell 4 outside, described nozzle on duty 1, it is inner that burner inner liner 5 is positioned at shell 4, premix section 2, burner inner liner 5 is provided with endless tube 10 and cyclone 3, endless tube 10 is connected with premix section 2, burner inner liner 5 is provided with nozzle 1 on duty, salband is formed between burner inner liner 5 and deflector 8, ring cavity C14 is formed between deflector 8 and shell 4, on shell 4, mounting guiding board 8 position circumference is distributed with vibration damping hole 17, whole combustion chamber is provided with two igniters 19, flame tube interconnector 20 is adopted to connect between two consecutive points firearms.Described premix section 2 is provided with four main gas outlets 18 and four main gas outlets 18 are evenly distributed in premix section 2.Described endless tube 10 is connected with main fuel gas inlet 12.
Operation principle of the present invention: air enters from air intake 16, flow through the salband that burner inner liner 5 is formed with deflector 8, premix section 2 is flowed through, at premix section 2 place, after combustion gas enters endless tube 10 from main fuel gas inlet 12 after entering ring cavity B13, premix section 2, main gas outlet 18 aperture flows out, now, after air and combustion gas complete preliminary premix, enter ring cavity A21, flow through cyclone 3 again and carry out secondary premix, the gaseous mixture after last premix enters territory, main combustion zone 15, combustion chamber and burns; Combustion gas on duty enters combustion zone on duty through nozzle 1 inner passage on duty, is burnt by diffusion way, improves combustion stability; For realizing the object of combustion chamber low emission, utilize the air control valve 7 being positioned at shell 4 outside that the partial air entered by air intake 16 is branched to igniter flame cylinder 5 afterbody through bypass pipe 6, do not participate in burning, namely air control valve 7 is utilized to regulate the air capacity entering primary combustion zone 15, the salband that burner inner liner 5 and deflector 8 are formed, for cooling flame cylinder 5 wall surface temperature.Combustion chamber adopts the Split type structure of 16 separate igniter, is convenient to realize the maintenance to each separate igniter and replacing; Combustion chamber adopts with nozzle 1 on duty, by introducing flame on duty, effectively can improve the stability of flame; Form resonator between deflector 8 and shell 4, on shell 4, mounting guiding board 8 position circumference is distributed with vibration damping hole 17, effectively reduces igniter pressure fluctuation, improves combustion chamber service life and combustibility; Combustion chamber adopts twice premix to combine, and realizes combustion gas and first mixes after-combustion with air, ensure combustion chambers burn performance; Conventional combustion room air control valve 7 is generally arranged in combustion chamber, is high-temperature component, its poor reliability, and safeguard comparatively difficulty, this device air control valve 7 is positioned at outside, combustion chamber, is non high temperature parts, effectively improves combustion chamber operational reliability and is convenient to safeguard and change; Combustion chamber utilizes air control valve 7 to regulate and enters combustion zone air capacity, effectively can realize the object of pollutant low emission; The salband that burner inner liner 5 and deflector 8 are formed, can effective cooling burner inner liner 5 wall surface temperature, raising combustion chamber service life; This device can be applicable on the industry gas turbine that electric power, petrochemical industry etc. take natural gas as fuel.
Claims (3)
1. one kind has the premixed low emission gas turbine combustion chamber of flame on duty, comprise igniter, shell, burner inner liner and premix section, it is characterized in that: combustion chamber is made up of 16 separate igniter, separate igniter comprises a shell (4), a burner inner liner (5), a nozzle on duty (1) and two air control valves (7), shell (4) is provided with deflector (8), bypass pipe (6) and air control valve (7), described bypass pipe (6) one end is installed on shell (4), bypass pipe (6) other end is installed on burner inner liner (5) afterbody, described air control valve (7) is connected with bypass pipe (6), and air control valve (7) is positioned at shell (4) outside, described nozzle on duty (1), it is inner that burner inner liner (5) is positioned at shell (4), premix section (2), burner inner liner (5) is provided with endless tube (10) and cyclone (3), endless tube (10) is connected with premix section (2), burner inner liner (5) is provided with nozzle on duty (1), salband is formed between burner inner liner (5) and deflector (8), ring cavity C(14 is formed) between deflector (8) and shell (4), shell (4) upper mounting guiding board (8) position circumference is distributed with vibration damping hole (17), whole combustion chamber is provided with two igniters (19), flame tube interconnector (20) is adopted to connect between two consecutive points firearms.
2. the premixed low emission gas turbine combustion chamber having flame on duty according to claim 1, is characterized in that: described premix section (2) is provided with four main gas outlets (18) and four main gas outlets (18) are evenly distributed in premix section (2).
3. the premixed low emission gas turbine combustion chamber having flame on duty according to claim 1, is characterized in that: described endless tube (10) is connected with main fuel gas inlet (12).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201511007113.5A CN105423341B (en) | 2015-12-30 | 2015-12-30 | There is the premixed low emission gas turbine combustion chamber of flame on duty |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201511007113.5A CN105423341B (en) | 2015-12-30 | 2015-12-30 | There is the premixed low emission gas turbine combustion chamber of flame on duty |
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| CN105423341A true CN105423341A (en) | 2016-03-23 |
| CN105423341B CN105423341B (en) | 2017-12-15 |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108375081A (en) * | 2018-03-06 | 2018-08-07 | 哈尔滨广瀚燃气轮机有限公司 | It is a kind of to fire double fuel ring-pipe type combustion chamber of the oil and gas as fuel |
| CN109519971A (en) * | 2018-12-28 | 2019-03-26 | 中国船舶重工集团公司第七0三研究所 | A kind of low emission gas turbine |
| US10415833B2 (en) | 2017-02-16 | 2019-09-17 | General Electric Company | Premixer for gas turbine combustor |
| CN111043627A (en) * | 2019-12-31 | 2020-04-21 | 新奥能源动力科技（上海）有限公司 | Combustion chamber structure and micro gas turbine |
| CN112483248A (en) * | 2020-12-03 | 2021-03-12 | 山东赛马力发电设备有限公司 | Compressor applied to gas turbine |
| CN115355528A (en) * | 2022-09-02 | 2022-11-18 | 中航通飞华南飞机工业有限公司 | Oblique flow type combustion chamber of turboprop engine |
| CN115355534B (en) * | 2022-09-05 | 2024-03-12 | 中国联合重型燃气轮机技术有限公司 | Gas turbine fuel mixing system and gas turbine |
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| US20100236245A1 (en) * | 2009-03-19 | 2010-09-23 | Johnson Clifford E | Gas Turbine Combustion System |
| CN102971510A (en) * | 2010-09-30 | 2013-03-13 | 三菱重工业株式会社 | Air recovery-type cooling structure for air-cooled gas turbine combustor |
| US20130291543A1 (en) * | 2012-05-02 | 2013-11-07 | Kwanwoo Kim | Acoustic Resonator Located at Flow Sleeve of Gas Turbine Combustor |
| CN103443542A (en) * | 2011-04-08 | 2013-12-11 | 阿尔斯通技术有限公司 | Gas turbine assembly and corresponding operating method |
| CN205261637U (en) * | 2015-12-30 | 2016-05-25 | 哈尔滨广瀚燃气轮机有限公司 | What have flame on duty mixes formula low emission combustion chamber in advance |
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2015
- 2015-12-30 CN CN201511007113.5A patent/CN105423341B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
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| US20100236245A1 (en) * | 2009-03-19 | 2010-09-23 | Johnson Clifford E | Gas Turbine Combustion System |
| CN102971510A (en) * | 2010-09-30 | 2013-03-13 | 三菱重工业株式会社 | Air recovery-type cooling structure for air-cooled gas turbine combustor |
| CN103443542A (en) * | 2011-04-08 | 2013-12-11 | 阿尔斯通技术有限公司 | Gas turbine assembly and corresponding operating method |
| US20130291543A1 (en) * | 2012-05-02 | 2013-11-07 | Kwanwoo Kim | Acoustic Resonator Located at Flow Sleeve of Gas Turbine Combustor |
| CN205261637U (en) * | 2015-12-30 | 2016-05-25 | 哈尔滨广瀚燃气轮机有限公司 | What have flame on duty mixes formula low emission combustion chamber in advance |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US10415833B2 (en) | 2017-02-16 | 2019-09-17 | General Electric Company | Premixer for gas turbine combustor |
| CN108375081A (en) * | 2018-03-06 | 2018-08-07 | 哈尔滨广瀚燃气轮机有限公司 | It is a kind of to fire double fuel ring-pipe type combustion chamber of the oil and gas as fuel |
| CN108375081B (en) * | 2018-03-06 | 2023-08-08 | 哈尔滨广瀚燃气轮机有限公司 | Dual-fuel annular combustion chamber using fuel oil and natural gas as fuel |
| CN109519971A (en) * | 2018-12-28 | 2019-03-26 | 中国船舶重工集团公司第七0三研究所 | A kind of low emission gas turbine |
| CN111043627A (en) * | 2019-12-31 | 2020-04-21 | 新奥能源动力科技（上海）有限公司 | Combustion chamber structure and micro gas turbine |
| CN112483248A (en) * | 2020-12-03 | 2021-03-12 | 山东赛马力发电设备有限公司 | Compressor applied to gas turbine |
| CN115355528A (en) * | 2022-09-02 | 2022-11-18 | 中航通飞华南飞机工业有限公司 | Oblique flow type combustion chamber of turboprop engine |
| CN115355534B (en) * | 2022-09-05 | 2024-03-12 | 中国联合重型燃气轮机技术有限公司 | Gas turbine fuel mixing system and gas turbine |
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|---|---|
| CN105423341B (en) | 2017-12-15 |
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